Optimal design of rocket nozzle parameters with consideration of gas-particle two phase flow effect

The design of the inner contour of solid propellant rocket motor nozzle is a key point to improve the efficiency of the nozzle. Based on Genetic Algorithms, a direct optimization method was used to optimize the key parameters determining the inner contour of the nozzle, to reduce the specific impulse loss and improve the efficiency of the engine. The specific impulse was obtained from two-phase flow calculation of the nozzle. Furthermore, a software interface was designed to automatically realize the contour optimization design for the general nozzle. As a result, good effect was obtained from the optimal computation for the current nozzle.